Experimental Research on Swept Shock Wave/Boundary Layer Interactions.
Abstract
Experiments were carried out to assess Mach number effects on boundary layer due to generic fin and swept compression corner geometries. An extensive set of fin interaction experiments was carried out at constant Reynolds number over the Mach number range of 2.5 to 4.0. Data thus far consist of surface flow visualization photographs and laser light-screen visualizations of flowfield structure. Additional experiments were conducted to assess the possibility that experimental data of this type might depend on the wind tunnel facility in which the experiments were performed. That was not found to be the case. Results of the parametric Mach number study revealed that Mach number effects over the range considered are essentially inviscid. These were accounted for simply by referencing measured quantities to the freestream Mach angle. The interaction growth with increasing shock strength was found to be nonlinear, contrary to previous results. Initial results from swept compression corner experiments are also reported. Keywords: High speed flows; Viscous inviscid interactions; Supersonic flow; Flow visualization; Fluid dynamics; Flow separation.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1987
- Accession Number
- ADA187250
Entities
People
- Gary S. Settles
Organizations
- Pennsylvania State University